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GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 257 AIRFOIL (goe257-il)
Reynolds number: 500,000
Max Cl/Cd: 88.88 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe257-il-500000-n5.txt
Download as CSV file: xf-goe257-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 257 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4255   0.10573   0.10355  -0.0090   1.0000   0.0075
  -9.000  -0.4232   0.10140   0.09924  -0.0111   1.0000   0.0077
  -8.750  -0.4238   0.09632   0.09418  -0.0136   1.0000   0.0080
  -8.500  -0.4196   0.09305   0.09094  -0.0154   1.0000   0.0082
  -8.250  -0.4131   0.09054   0.08845  -0.0168   1.0000   0.0084
  -8.000  -0.4088   0.08780   0.08573  -0.0183   1.0000   0.0087
  -7.750  -0.4028   0.08430   0.08225  -0.0213   0.9951   0.0090
  -7.500  -0.3874   0.07925   0.07718  -0.0280   0.9719   0.0092
  -7.250  -0.3715   0.07387   0.07176  -0.0348   0.9503   0.0095
  -7.000  -0.3567   0.06830   0.06612  -0.0409   0.9271   0.0099
  -6.750  -0.3407   0.06073   0.05838  -0.0484   0.9042   0.0105
  -6.500  -0.3215   0.05541   0.05288  -0.0530   0.8775   0.0112
  -6.250  -0.3016   0.05342   0.05072  -0.0544   0.8385   0.0116
  -6.000  -0.2803   0.05028   0.04729  -0.0565   0.7898   0.0123
  -5.750  -0.2492   0.03775   0.03410  -0.0638   0.7659   0.0146
  -5.500  -0.2251   0.03676   0.03290  -0.0645   0.7420   0.0150
  -5.250  -0.2004   0.03603   0.03201  -0.0651   0.7250   0.0155
  -5.000  -0.1736   0.03383   0.02958  -0.0662   0.7126   0.0163
  -4.750  -0.1396   0.02557   0.02046  -0.0679   0.7048   0.0195
  -4.500  -0.1131   0.02469   0.01946  -0.0686   0.6962   0.0200
  -4.250  -0.0858   0.02381   0.01844  -0.0691   0.6889   0.0205
  -4.000  -0.0576   0.02252   0.01694  -0.0697   0.6827   0.0212
  -3.750  -0.0288   0.02116   0.01535  -0.0701   0.6764   0.0223
  -3.500   0.0006   0.01962   0.01350  -0.0704   0.6709   0.0235
  -3.250   0.0300   0.01829   0.01189  -0.0707   0.6650   0.0240
  -3.000   0.0591   0.01728   0.01062  -0.0710   0.6590   0.0245
  -2.750   0.0883   0.01677   0.00992  -0.0712   0.6531   0.0251
  -2.500   0.1174   0.01612   0.00906  -0.0715   0.6469   0.0257
  -2.250   0.1463   0.01497   0.00772  -0.0718   0.6417   0.0260
  -2.000   0.1752   0.01399   0.00663  -0.0721   0.6361   0.0265
  -1.750   0.2039   0.01337   0.00593  -0.0724   0.6303   0.0269
  -1.500   0.2327   0.01289   0.00540  -0.0726   0.6249   0.0274
  -1.250   0.2614   0.01248   0.00494  -0.0729   0.6183   0.0278
  -1.000   0.2901   0.01213   0.00454  -0.0731   0.6109   0.0281
  -0.750   0.3188   0.01182   0.00419  -0.0733   0.6013   0.0284
  -0.500   0.3475   0.01158   0.00392  -0.0736   0.5911   0.0291
  -0.250   0.3761   0.01136   0.00366  -0.0738   0.5813   0.0297
   0.000   0.4049   0.01113   0.00339  -0.0740   0.5715   0.0296
   0.250   0.4337   0.01094   0.00316  -0.0743   0.5613   0.0296
   0.500   0.4624   0.01080   0.00297  -0.0745   0.5480   0.0296
   0.750   0.4911   0.01069   0.00281  -0.0748   0.5334   0.0299
   1.000   0.5198   0.01062   0.00269  -0.0750   0.5200   0.0302
   1.250   0.5485   0.01058   0.00260  -0.0753   0.5056   0.0308
   1.500   0.5769   0.01060   0.00254  -0.0755   0.4881   0.0317
   1.750   0.6053   0.01065   0.00251  -0.0757   0.4717   0.0327
   2.000   0.6336   0.01071   0.00252  -0.0760   0.4594   0.0335
   2.250   0.6619   0.01080   0.00255  -0.0762   0.4464   0.0342
   2.500   0.6901   0.01092   0.00259  -0.0764   0.4316   0.0364
   2.750   0.7182   0.01103   0.00266  -0.0766   0.4186   0.0402
   3.000   0.7464   0.01114   0.00275  -0.0768   0.4080   0.0433
   3.250   0.7698   0.00918   0.00291  -0.0765   0.3999   1.0000
   3.500   0.7979   0.00935   0.00302  -0.0766   0.3906   1.0000
   3.750   0.8261   0.00950   0.00314  -0.0768   0.3798   1.0000
   4.000   0.8540   0.00968   0.00329  -0.0770   0.3660   1.0000
   4.250   0.8817   0.00992   0.00344  -0.0772   0.3444   1.0000
   4.500   0.9088   0.01023   0.00362  -0.0773   0.3104   1.0000
   5.000   0.9589   0.01166   0.00444  -0.0773   0.2044   1.0000
   5.250   0.9856   0.01202   0.00473  -0.0774   0.1885   1.0000
   5.500   1.0120   0.01240   0.00503  -0.0774   0.1667   1.0000
   5.750   1.0371   0.01299   0.00542  -0.0774   0.1290   1.0000
   6.000   1.0586   0.01418   0.00624  -0.0769   0.0542   1.0000
   6.250   1.0840   0.01464   0.00667  -0.0767   0.0406   1.0000
   6.500   1.1078   0.01534   0.00723  -0.0764   0.0178   1.0000
   6.750   1.1329   0.01582   0.00777  -0.0761   0.0135   1.0000
   7.000   1.1580   0.01625   0.00826  -0.0759   0.0123   1.0000
   7.250   1.1825   0.01674   0.00883  -0.0756   0.0112   1.0000
   7.500   1.2062   0.01732   0.00949  -0.0751   0.0102   1.0000
   7.750   1.2283   0.01807   0.01035  -0.0744   0.0092   1.0000
   8.000   1.2500   0.01881   0.01118  -0.0737   0.0085   1.0000
   8.250   1.2725   0.01940   0.01184  -0.0731   0.0079   1.0000
   8.500   1.2935   0.02012   0.01264  -0.0723   0.0074   1.0000
   8.750   1.3133   0.02091   0.01351  -0.0713   0.0070   1.0000
   9.000   1.3319   0.02176   0.01443  -0.0702   0.0066   1.0000
   9.250   1.3486   0.02271   0.01547  -0.0688   0.0063   1.0000
   9.500   1.3606   0.02397   0.01683  -0.0668   0.0061   1.0000
   9.750   1.3684   0.02543   0.01839  -0.0641   0.0058   1.0000
  10.000   1.3791   0.02652   0.01959  -0.0619   0.0057   1.0000
  10.250   1.3865   0.02766   0.02084  -0.0591   0.0055   1.0000
  10.500   1.3907   0.02893   0.02222  -0.0561   0.0053   1.0000
  10.750   1.3951   0.03038   0.02378  -0.0535   0.0051   1.0000
  11.000   1.3998   0.03197   0.02549  -0.0513   0.0049   1.0000
  11.250   1.4036   0.03377   0.02741  -0.0495   0.0047   1.0000
  11.500   1.4065   0.03581   0.02956  -0.0479   0.0046   1.0000
  11.750   1.4093   0.03803   0.03189  -0.0467   0.0045   1.0000
  12.000   1.4116   0.04043   0.03441  -0.0458   0.0044   1.0000
  12.250   1.4133   0.04305   0.03714  -0.0452   0.0043   1.0000
  12.500   1.4147   0.04580   0.03999  -0.0448   0.0042   1.0000
  12.750   1.4147   0.04877   0.04307  -0.0445   0.0041   1.0000
  13.000   1.4134   0.05195   0.04637  -0.0443   0.0040   1.0000
  13.250   1.4102   0.05537   0.04990  -0.0441   0.0040   1.0000
  13.500   1.4048   0.05910   0.05376  -0.0439   0.0039   1.0000
  13.750   1.3965   0.06324   0.05805  -0.0437   0.0038   1.0000
  14.000   1.3921   0.06701   0.06198  -0.0439   0.0038   1.0000
  14.250   1.3866   0.07104   0.06617  -0.0443   0.0038   1.0000
  14.500   1.3803   0.07534   0.07063  -0.0449   0.0037   1.0000
  14.750   1.3728   0.07994   0.07540  -0.0458   0.0037   1.0000
  15.000   1.3642   0.08487   0.08050  -0.0470   0.0037   1.0000
  15.250   1.3548   0.09012   0.08592  -0.0485   0.0036   1.0000
  15.500   1.3442   0.09577   0.09175  -0.0503   0.0036   1.0000
  15.750   1.3328   0.10172   0.09787  -0.0525   0.0036   1.0000
  16.000   1.3204   0.10805   0.10438  -0.0550   0.0036   1.0000
  16.250   1.3075   0.11468   0.11118  -0.0579   0.0035   1.0000
  16.500   1.2939   0.12169   0.11835  -0.0612   0.0035   1.0000
  16.750   1.2799   0.12900   0.12583  -0.0648   0.0035   1.0000
  17.000   1.2655   0.13670   0.13369  -0.0690   0.0035   1.0000
  17.250   1.2514   0.14471   0.14185  -0.0734   0.0035   1.0000
  17.500   1.2370   0.15319   0.15049  -0.0784   0.0035   1.0000
  17.750   1.2223   0.16217   0.15961  -0.0838   0.0035   1.0000
  18.000   1.2081   0.17138   0.16895  -0.0895   0.0036   1.0000
  18.250   1.1935   0.18126   0.17896  -0.0956   0.0036   1.0000
  18.500   1.1777   0.19230   0.19012  -0.1024   0.0036   1.0000
  18.750   1.1581   0.20612   0.20402  -0.1106   0.0037   1.0000
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